公开(公告)号：WO02052136A3

公开(公告)日：2003-04-10

申请号：PCT/US0147827

申请日：2001-12-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALBERO JOSE ,  DUSSAULT RICHARD ,  THOMPSON ROBERT G ,  GERMAIN PATRICK ,  SAHM MICHAEL K ,  TREMAINE ERIC

IPC: F02C7/277 ,  F02C7/32 ,  F02K3/06 ,  F02K3/12 ,  B64C31/00

CPC classification number: F02K3/12 ,  F02C7/277 ,  F02C7/32 ,  F02K3/06 ,  F05D2220/50 ,  Y02T50/671

Abstract: A main engine (14) mounted auxiliary power unit (30) comprises an auxiliary power unit (31) integrated with a primary gas turbine engine (14) into a single power plant suited for aircraft applications. The auxiliary power unit (30) can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit (30) provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit (30) to the tail section of the aircraft.

Abstract translation: 安装有辅助动力单元（30）的主发动机（14）包括与主要燃气涡轮发动机（14）整合成适用于飞行器应用的单个动力装置的辅助动力单元（31）。 辅助动力单元（30）可以安装在主发动机的发动机核心舱内或主发动机尾部中心体上。 辅助动力单元（30）的集成通过消除将辅助动力单元（30）安装到飞行器尾部的需要来为空中装置提供安装和认证成本节省。

公开(公告)号：WO02066324A3

公开(公告)日：2003-03-27

申请号：PCT/US0204956

申请日：2002-02-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALBERO JOSE ,  BRUNO LOUIS J ,  DUSSAULT RICHARD ,  LENTS CHARLES E ,  THRESHER WAYNE A ,  SAHM MICHAEL K ,  THOMPSON ROBERT G

IPC: B64D13/06 ,  B64D15/04 ,  B64D27/16 ,  B64D41/00 ,  F02C7/32 ,  B64D35/00

CPC classification number: B64D15/04 ,  B64D13/06 ,  B64D27/16 ,  B64D41/00 ,  B64D2013/0611 ,  B64D2013/064 ,  B64D2013/0644 ,  F02C7/32 ,  F05D2220/50 ,  Y02T50/44 ,  Y02T50/56 ,  Y02T50/671

Abstract: The present invention relates to an integrated aircraft system which comprises an aircraft frame (4), a primary gas turbine engine (14) mounted within the nacelle cowl (12), a secondary power system (30) incorporated within the nacelle cowl and being driven by a flow of air created by or through the engine, and an electrical power and cooling unit for supplying electrical power and cabin cooling air. The electrical power and cooling unit is pneumatically driven by engine bleed air.

Abstract translation: 本发明涉及一种集成飞行器系统，其包括飞机机架（4），安装在机舱罩（12）内的主要燃气涡轮发动机（14），并入机舱罩内并被驱动的次级动力系统（30） 通过由发动机产生的或通过发动机产生的空气流，以及用于供应电力和舱室冷却空气的电力和冷却单元。 电力和冷却单元由发动机排放气体气动驱动。